An unmanned aerial vehicle, having a main body comprising at least an elongate backbone with a forward end piece and a rearward end piece. The end pieces are wider than the backbone and comprise coupling facilities for respective rotor arms, each said rotor arm configured for supporting motor and propeller assemblies. The unmanned aerial vehicle further comprises a pair of elongated batteries. The end pieces and at least a portion of the backbone form receptacles on both sides of the backbone for releasably receiving respective electric batteries, wherein the batteries, backbone and end pieces form an elongate and substantially rectangular body assembly.

Unmanned aerial vehicles and frames thereof are disclosed. The unmanned aerial vehicle includes a frame and a control module. The frame includes a central frame, a first arm set, and a second arm set. Each of the first arm set and the second arm set includes a second arm assembly, a third arm assembly, and a first arm assembly. The first arm assembly is located between the second arm assembly and the third arm assembly. The first arm assembly includes a first rotor assembly. The second arm assembly includes a second rotor assembly. The third arm assembly includes a third rotor assembly. In an output direction of downward-propelling wind fields, one of a rotation plane of the first rotor assembly, a rotation plane of the second rotor assembly, and a rotation plane of the third rotor assembly is located at a different position from the other two.

Disclosed is a drone configured for multiple uses. The drone may include a body and a sensor configured to be attached to the body. Further, the drone may include a plurality of arms configured to be attached to the body. Further, a first end of an arm of the plurality of arms may be attached to the body at a first movable joint. Further, the arm may include a first part connected to the first movable joint. Further, the arm may include a second part attached to the first part at a second movable joint. Further, the arm may include a powered rotor including a shaft configured to provide rotatory motion. Further, the powered rotor may be attached to one or more of the first part and the second part. Further, the drone may include a plurality of propeller blades attached to the shaft.

A method of delivering heavy payload using an autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

The technology described herein relates to autonomous aerial vehicle technology and, more specifically, to autonomous unmanned aerial vehicle with folding collapsible arms. In some embodiments, a UAV including a central body, a plurality of rotor arms, and a plurality of hinge mechanisms is disclosed. The plurality of rotor arms each include a rotor unit at a distal end of the rotor arm. The rotor units are configured to provide propulsion for the UAV. The plurality of hinge mechanisms mechanically attach (or couple) proximal ends of the plurality of rotor arms to the central body. Each hinge mechanism is configured to rotate a respective rotor arm of the plurality of rotor arms about an axis of rotation that is at an oblique angle relative to a vertical median plane of the central body to transition between an extended state and a folded state.

The technology described herein relates to autonomous aerial vehicle technology and, more specifically, to image stabilization systems for autonomous aerial vehicles. In some embodiments, a UAV including a central body, an image capture assembly that couples the image capture assembly to the central body. The image stabilization assembly is configured to provide structural protection and support around the image capture assembly while passively isolating the image capture assembly from vibrations and other motion of the central body while the UAV is in flight.

A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extendable from the central body using one or more actuators. Each of the plurality of arms is configured to support one or more propulsion units. One arm of the plurality of arms is configured to connect to one of the one or more actuators via a linkage mechanism. The one of the one or more actuators is configured to actuate the linkage mechanism between (1) a first dead center position for securing the one arm when the one arm is extended away from the central body in a flight configuration and (2) a second dead center position for securing the one arm when the one arm is folded substantially parallel to the central body in a compact configuration.

An unmanned aerial vehicle includes a fuselage body and a lift mechanism. The lift mechanism includes a rotor blade assembly and a rotary driving member and defines an axis of rotation. The lift being mechanism is coupled to the fuselage body. The rotary driving member is configured to controllably rotate the rotor blade assembly about the axis of rotation. The rotor blade assembly includes at least one rotor blade. The at least one rotor blade including a vortex generator defined along an upper surface of the rotor blade.

A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members and an elongated boom arm. Each of the boom hinges pivot the boom arms between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position.